CN-121973948-A - Portable aircraft automatic throttle S electric valve in-situ test system

CN121973948ACN 121973948 ACN121973948 ACN 121973948ACN-121973948-A

Abstract

The invention discloses a portable aircraft automatic throttle S electric valve in-situ test system, which relates to the technical field of tests and comprises the following steps of screening and obtaining target actual measurement data of an electric valve to be tested based on a test characteristic identification library; the method comprises the steps of obtaining actual test indexes of target actual measurement data, obtaining abnormal test data according to the actual test indexes and standard test parameters, obtaining test deviation coefficients of the abnormal test data according to actual parameter measurement values, obtaining first environment test coefficients of the test environment according to the abnormal data parameters and the test deviation coefficients of the abnormal test data in the test environment, marking an electric gate corresponding to the abnormal test data as an abnormal electric gate, obtaining second environment test coefficients of the test environment according to abnormal equipment parameters of the abnormal electric gate in the test environment, and providing clear basis for maintenance or replacement of the electric gate.

Inventors

Shi Jinshou
LI LINJIE
ZHU YUMENG
WANG JINGRU
CHEN XUEZHI
Guan Xinnan
ZHANG BOYI
ZHANG HAOXUAN

Assignees

北京科技职业大学

Dates

Publication Date: 20260505
Application Date: 20251212

Claims (9)

1. A portable aircraft automatic throttle S electric door in-situ test system, comprising: the screening module is used for screening and obtaining target actual measurement data of the electric gate to be tested based on the test characteristic identification library; the first processing module is used for acquiring actual test indexes of the target actual measurement data, acquiring abnormal test data according to the actual test indexes and standard test parameters and acquiring test deviation coefficients of the abnormal test data according to actual parameter measurement values; The second processing module is used for obtaining a first environment test coefficient of the test environment according to the abnormal data parameters and the test deviation coefficients of the abnormal test data in the test environment, marking the electric gate corresponding to the abnormal test data as an abnormal electric gate, and obtaining a second environment test coefficient of the test environment according to the abnormal equipment parameters of the abnormal electric gate in the test environment; The first output module is used for obtaining a first test qualification degree of the test environment according to the first environment test coefficient and the second environment test coefficient; and the second output module is used for obtaining equipment abnormality information parameters of the abnormal electric gate corresponding to the abnormality test data and obtaining a second test qualification degree of the abnormal electric gate according to the equipment abnormality information parameters.
2. The portable aircraft automatic throttle S-valve in-situ test system according to claim 1, wherein the target measured data of the valve to be tested is obtained by screening based on a test feature identification library, and specifically comprises the following steps: Performing identification matching on the actually measured data of the electric gate to be tested according to the core test identification code of the test feature identification library to obtain a target test identification code; And carrying out data classification extraction on the measured data according to the target test identification code to obtain target measured data corresponding to the target test identification code.
3. The portable aircraft automatic throttle S-valve in-situ test system of claim 1, wherein the abnormal test data is obtained according to the actual test index and the standard test parameters, and specifically comprises the following steps: the actual test index comprises an actual parameter measured value corresponding to target actual measurement data, wherein the actual parameter measured value corresponds to a parameter qualification threshold of the test item type; And if the actual parameter measured value of the actually measured data exceeds the parameter qualification threshold corresponding to the standard test parameter, judging that the actually measured data is abnormal test data.
4. The portable aircraft automatic throttle S-valve in-situ test system of claim 3, wherein the test deviation coefficient of the anomaly test data is obtained based on the actual parameter measurement, comprising the steps of: marking the actual parameter measurement value exceeding the parameter qualification threshold as a deviation parameter value; and obtaining a test deviation coefficient of the abnormal test data according to the deviation parameter value and the parameter qualification threshold value.
5. The portable aircraft automatic throttle S-valve in-situ test system of claim 4, wherein the first environmental test coefficient of the test environment is obtained from the anomaly data parameters and the test deviation coefficients of the anomaly test data in the test environment, comprising the steps of: Setting item type weights of the abnormal test data according to the test item types corresponding to the abnormal test data; obtaining a comprehensive deviation coefficient of the abnormal test data according to the test deviation coefficient of the abnormal test data and the project type weight, wherein the abnormal data parameters comprise the number of abnormal data of the abnormal test data in the test environment; Obtaining a first deviation evaluation coefficient according to the number of abnormal data and the comprehensive deviation coefficient; Acquiring the total number of measured data of the electric gate to be tested in the test environment, and acquiring a second deviation evaluation coefficient of the test environment according to the total number of measured data and the number of abnormal data; And obtaining a first environment test coefficient of the test environment according to the first deviation evaluation coefficient and the second deviation evaluation coefficient.
6. The portable aircraft automatic throttle S-valve in-situ test system of claim 5, wherein the second environmental test factor of the test environment is obtained from the abnormal equipment parameters of the abnormal valve in the test environment, comprising the steps of: the abnormal equipment parameters comprise the number of abnormal equipment and the number of historical abnormal equipment of an abnormal electric door in the test environment; Obtaining the equipment abnormal change rate of the abnormal electric gate in the test environment according to the historical abnormal equipment number and the abnormal equipment number; And obtaining a second environment test coefficient of the test environment according to the abnormal change rate of the equipment.
7. The portable aircraft automatic throttle S-valve in-situ test system of claim 6, wherein the first test qualification level of the test environment is obtained based on the first environmental test coefficient and the second environmental test coefficient, comprising the steps of: setting a first evaluation weight and a second evaluation weight; and obtaining a first test qualification degree corresponding to the test environment according to the first evaluation weight, the first environment test coefficient, the second evaluation weight and the second environment test coefficient.
8. The portable aircraft automatic throttle S-electric door in-situ test system of claim 7, wherein the equipment anomaly information parameter comprises a continuous anomaly frequency.
9. The portable aircraft automatic throttle S-valve in-situ test system of claim 8, wherein the second test eligibility level of the abnormal valve is obtained according to the equipment abnormality information parameter, and specifically comprising the steps of: Obtaining the equipment stability coefficient of the abnormal electric gate according to the continuous abnormal frequency; accumulating and calculating the comprehensive deviation coefficient corresponding to the abnormal test data according to the times of the abnormal data to obtain the total deviation coefficient of the equipment of the abnormal electric gate; And obtaining a second test qualification degree of the abnormal electric gate according to the equipment stability coefficient and the equipment total deviation coefficient.

Description

Portable aircraft automatic throttle S electric valve in-situ test system Technical Field The invention relates to the technical field of testing, in particular to a portable airplane automatic throttle S-type electric door in-situ testing system. Background In an automatic throttle system of an aircraft, an S electric valve is used as a key component, and the performance of the S electric valve directly influences the power control and the flight safety of the aircraft. Traditional electric gate test relies on manual operation more, because lack unified sign storehouse support, consequently the data confusion or the omission appears easily, leads to the inefficiency of test. In the prior art, the abnormal data is judged by experience, so that the deviation degree is difficult to accurately quantify, the accuracy of abnormal identification is insufficient, the traditional mode usually only focuses on the abnormality of the data layer, the influence of equipment abnormal change on the test environment is ignored, the evaluation dimension is single, the evaluation of the abnormal electric gate is lack of comprehensive consideration of stability, total deviation degree and other multidimensional factors, and the actual condition of the electric gate is difficult to comprehensively reflect. These problems make it difficult for conventional test methods to meet the requirements of modern aircraft electric door testing both in terms of comprehensiveness and efficiency. Disclosure of Invention Aiming at the defects existing in the prior art, the invention aims to provide a portable airplane automatic throttle S electric door in-situ test system. In order to achieve the above purpose, the present invention provides the following technical solutions: a portable aircraft automatic throttle S electric door in-situ test system comprising: the screening module is used for screening and obtaining target actual measurement data of the electric gate to be tested based on the test characteristic identification library; the first processing module is used for acquiring actual test indexes of the target actual measurement data, acquiring abnormal test data according to the actual test indexes and standard test parameters and acquiring test deviation coefficients of the abnormal test data according to actual parameter measurement values; The second processing module is used for obtaining a first environment test coefficient of the test environment according to the abnormal data parameters and the test deviation coefficients of the abnormal test data in the test environment, marking the electric gate corresponding to the abnormal test data as an abnormal electric gate, and obtaining a second environment test coefficient of the test environment according to the abnormal equipment parameters of the abnormal electric gate in the test environment; The first output module is used for obtaining a first test qualification degree of the test environment according to the first environment test coefficient and the second environment test coefficient; and the second output module is used for obtaining equipment abnormality information parameters of the abnormal electric gate corresponding to the abnormality test data and obtaining a second test qualification degree of the abnormal electric gate according to the equipment abnormality information parameters. Optionally, screening based on a test feature identification library to obtain target actual measurement data of the electric gate to be tested, wherein the method specifically comprises the following steps: Performing identification matching on the actually measured data of the electric gate to be tested according to the core test identification code of the test feature identification library to obtain a target test identification code; And carrying out data classification extraction on the measured data according to the target test identification code to obtain target measured data corresponding to the target test identification code. The core test identification codes of the test feature identification library are used for carrying out identification matching on the actually measured data of the electric gate to be tested, so that the target test identification codes can be accurately determined, the accuracy of data screening is ensured, error screening caused by unclear data identification is avoided, and a reliable data base is laid for subsequent test work. And secondly, data classification extraction is carried out on the measured data according to the target test identification code, so that efficient screening of the target measured data is realized, the data processing efficiency is greatly improved, and the complicated process and time cost of manual screening are reduced. The accurate and efficient screening mode ensures that the whole testing system has higher reliability and timeliness in the data acquisition link, is beneficial to the successful development of links such